31 Airworthiness Directives: 18 airplane, 7 rotorcraft, 1 engine, 4 propeller, 1 various.
AD 2003-02-51 · published Feb 5, 2003, effective Feb 10, 2003
Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-02-51 that was sent previously to all known U.S. owners and operators of Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes by individual notices. This AD requires an airplane flight manual (AFM) revision to introduce new quantity limitations for the center fuel tank and associated procedures; to limit flight to within 30 minutes of a suitable alternative airport; and to limit the center tank fuel quantity to 1,500 lbs. (680 kgs.) maximum at takeoff. This action is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. The actions specified by this AD are intended to detect and correct discrepancies in the fuel distribution system, which could cause the center tank to overfill and fuel to leak from the center tank vent system or to become inaccessible, and could result in engine fuel starvation.
AD 2003-03-14 · published Feb 5, 2003, effective Mar 8, 2003
Piaggio Aero Industries S.p.A. Model P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Piaggio Aero Industries S.p.A. (Piaggio) Model P-180 airplanes. This AD requires you to inspect and determine whether any firewall shutoff or crossfeed valve with a serial number in a certain range is installed and requires you to replace any valve that has a serial number within this range. This AD allows the pilot to check the logbook and does not require the inspection and replacement requirement if the check shows that one of these valves is definitely not installed. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent a faulty firewall shutoff or crossfeed valve from developing cracks and leaking fuel. This could result in an engine fire.
AD 2003-03-16 · published Feb 5, 2003, effective Feb 20, 2003
Airbus Model A330-223, -321, -322, and -323 Series Airplanes Equipped With Pratt & Whitney Model PW4164, PW4168, or PW4168A Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-223, -321, -322, and -323 series airplanes equipped with Pratt & Whitney Model PW4164, PW4168, or PW4168A engines. This action requires modification of the primary structure of the engine pylons, and replacement of the thrust reverser locking actuators with new, improved locking actuators. This action is necessary to prevent reduced structural integrity of the primary structure of the engine pylons, and uncommanded deployment of the thrust reversers, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-03-17 · published Feb 5, 2003, effective Mar 12, 2003
Dornier Model 328-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires replacement of the screws in the aileron, rudder, and elevator trim tabs with new screws; and removal and re-installation of screws in the aileron, elevator, and rudder trim tabs and the rudder spring tab; as applicable. This action is necessary to prevent reduced structural integrity of the screws in the aileron, elevator, and rudder trim tabs and the rudder spring tab, due to countersinks that were not manufactured correctly, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-03-18 · published Feb 5, 2003, effective Feb 5, 2003
Raytheon Aircraft Company Beech Models 1900, 1900C, and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to perform control column sweep and stop bolt inspections to verify full elevator travel to the primary up and down stops and that the stop bolt length is not excessive, re-rig the elevator control system if the airplane does not pass the control column sweep and stop inspections, and do a more detailed inspection at a later time if the airplane does pass the inspection. This AD also requires you to report the results of certain inspections. This AD is the result of recent ground testing and a review of the rigging procedures of a Raytheon Beech Model 1900D airplane, which reveals that the elevator control system could be mis- rigged to restrict elevator travel if current maintenance procedures are not properly followed. In these instances, it may appear to the crew that they have full elevator control column movement. However, the elevator may not have full travel. Such restricted travel may remain undetected until the airplane is operated in a loading condition that requires full elevator authority to control the pitch. The actions specified by this AD are intended to detect and correct any mis-rigged elevator control system, which could lead to insufficient elevator control authority and loss of control of the airplane.
AD 2003-03-19 · published Feb 5, 2003, effective Feb 20, 2003
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747 series airplanes. This action requires a one-time inspection of the fuselage skin of the aft lower body for certain repair doublers, and follow-on inspections and corrective actions if such doublers are installed. For certain airplanes, this action includes optional repetitive inspections of the fuselage skin for scratches or cracking. This action is necessary to find and fix possible fatigue cracking of the fuselage skin concealed under certain repair doublers, which could result in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-03-22 · published Feb 5, 2003, effective Mar 12, 2003
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes, that requires installing speedbrake limitation placards in the flight compartment, and revising the Limitations Section of the Airplane Flight Manual to ensure the flightcrew is advised not to extend the speedbrake lever beyond the flight detent. For certain airplanes, this AD requires modifying the elevator and elevator tab assembly. This action is necessary to prevent severe vibration of the elevator and elevator tab assembly, which could result in severe damage to the horizontal stabilizer followed by possible loss of the elevator tab and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-03-23 · published Feb 7, 2003, effective Feb 24, 2003
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires replacement of the horizontal stabilizer control units (HSCUs) with new upgraded HSCUs, and corrective actions if necessary. This action is necessary to prevent reversal of the pilot's pitch trim command for the horizontal stabilizer, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-04-02 · published Feb 19, 2003, effective Apr 4, 2003
APEX Aircraft Model CAP 10B Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-12- 10 and AD 99-21-23, which currently apply to APEX Aircraft (APEX) Model CAP 10B airplanes. AD 98-12-10 requires installing an inspection opening in the wing, repetitively inspecting the upper and lower wing spars for structural cracking, and, if any cracks are found, repairing the cracks in accordance with a repair method. AD 99-21-23 requires restricting the entry speed for performing flick maneuvers to 97 knots, inserting a copy of the AD into the Limitations Section of the CAP 10B flight manual, and fabricating and installing a placard (in the cockpit of the airplane within the pilot's clear view) that indicates this limitation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. This AD retains the wing modification and repair requirements from AD 98-12-10. This AD also incorporates new repetitive inspection procedures, further reduces the flick maneuver speed specified in AD 99-21-23, and temporarily reduces the load factor limits prior to the initial inspection. The actions specified by this AD are intended to provide the flight information necessary to the pilot so that excessive speed is not used during aerobatic maneuvers and to detect and correct structural cracks in the wing spar, which could result in the wing separating from the airplane. Such failure could lead to loss of control of the airplane.
AD 2003-04-03 · published Feb 19, 2003, effective Apr 7, 2003
SOCATA-Groupe AEROSPATIALE Models TB 9, TB 10, TB 20, TB 21, and TB 200 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe AEROSPATIALE (Socata) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This AD requires you to repetitively inspect the aileron control gimbal joint for correct alignment and correct operation, and replace any misaligned or defective gimbal joint. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent failure of the aileron control gimbal joint. Such failure could lead to loss of control of the airplane.
AD 2003-04-07 · published Feb 19, 2003, effective Apr 7, 2003
British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes. This AD requires you to repetitively inspect the horizontal and vertical stabilizer attachment fittings and associated hardware for corrosion and wear (damage). If damage is found, this AD also requires you to repair or replace the damaged parts. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct damage on the horizontal and vertical stabilizer attachment fittings and associated hardware, which could result in failure of the attachment fittings. Such failure could lead to flutter and subsequent structural failure of the empennage.
AD 2003-04-08 · published Feb 19, 2003, effective Apr 11, 2003
Piaggio Aero Industries S.p.A. Model P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Piaggio Aero Industries S.p.A. (Piaggio) Model P-180 airplanes. This AD requires you to install a placard on the inside of the lavatory door that prohibits occupying the lavatory seat during takeoff and landing. This AD also requires you to incorporate a temporary revision into the Limitations Section of the pilot operating handbook/airplane flight manual (POH/AFM). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent passengers from occupying the lavatory seat during takeoff and landing. The lavatory/cabin partition could fail and lead to passenger injury in an emergency situation.
AD 2003-04-10 · published Feb 28, 2003, effective Apr 4, 2003
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time general visual inspection to find wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This action is necessary to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin. This action is intended to address the identified unsafe condition.
AD 2003-04-18 · published Feb 28, 2003, effective Apr 4, 2003
McDonnell Douglas Model MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires measuring the length of the wear indicator on the brake stack of the main landing gear (MLG) brake assembly to determine the degree of wear, and follow-on actions. This action also requires eventual replacement of the existing MLG brake assembly with a new, improved or modified assembly, which constitutes terminating action for any repetitive actions being performed per this AD. The actions specified by this AD are intended to prevent failure of the MLG brakes and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing. This action is intended to address the identified unsafe condition.
AD 2003-04-19 · published Feb 28, 2003, effective Apr 4, 2003
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time general visual inspection to detect any missing attachment bolts in the replaceable frame struts, and corrective actions, if necessary. This action is necessary to prevent excessive deformation of the floor structure in the event of rapid decompression in the lower cargo hold due to missing attachment bolts in the replaceable frame struts. Such deformation may result in the flight and engine control cables becoming jammed, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-04-20 · published Feb 28, 2003, effective Apr 4, 2003
Raytheon Model DH.125, HS.125, and BH.125 Series Airplanes; Model BAe.125 Series 800A, 800A (C-29A), 800A (U-125), 800B, 1000A, and 1000B Airplanes; and Model Hawker 800, 800 (including variant U-125A), 1000, and 800XP Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series airplanes; and Model Hawker 800, Hawker 800 (including variant U-125A), Hawker 800XP, and Hawker 1000 airplanes; that currently requires an inspection for cracking or corrosion of the cylinder head lugs of the main landing gear (MLG) actuator and follow-on/corrective actions. This amendment expands the applicability of the existing AD to add an airplane model and further clarify the applicability and, for certain airplanes, to clarify the compliance time of the inspection requirements. This action is necessary to prevent separation of the cylinder head lugs, which could prevent the MLG from extending and result in a partial gear-up landing. This action is intended to address the identified unsafe condition.
AD 2003-04-21 · published Feb 28, 2003, effective Apr 4, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 440) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 440) series airplanes, that requires replacement of the overwing emergency exit placards, door weight placards, and no baggage placards with new placards. This action is necessary to prevent the inability of a passenger to open and dispose of the overwing emergency exit door during an emergency evacuation due to incorrect placards. This action is intended to address the identified unsafe condition.
AD 2003-04-24 · published Feb 28, 2003, effective Mar 17, 2003
McDonnell Douglas Model 717-200 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model 717-200 airplanes. This action requires a one-time inspection for cracking of the support fitting assemblies and stop pads of the main spoiler actuators, and follow-on actions. This action is necessary to find and fix cracking of the support fitting assemblies of the main spoiler actuator, which could result in damage of adjacent structure such as the rear spar or upper skin panel, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-04-04 · published Feb 19, 2003, effective Mar 26, 2003
Robinson Helicopter Company Model R22 Helicopters
This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (RHC) Model R22 helicopters that requires inspecting the tail rotor pitch control assembly for roughness or binding of the pitch control bearings (bearings) by hand-rotating the pitch control bearing housing (housing). If the housing does not rotate freely, the AD requires replacing the unairworthy pitch control assembly with an airworthy unit. This amendment is prompted by reports of failure of the tail rotor pitch control assembly due to improperly lubricated bearings on the RHC Model R22 helicopters. The actions specified by this AD are intended to detect corrosion of the bearings and to prevent bearing failure and subsequent loss of directional control of the helicopter.
AD 2003-04-05 · published Feb 19, 2003, effective Mar 26, 2003
Robinson Helicopter Company Model R44 Helicopters
This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (RHC) Model R44 helicopters that requires inspecting the tail rotor pitch control assembly for roughness or binding of the pitch control bearings (bearings) by hand-rotating the pitch control bearing housing (housing). If the housing does not rotate freely, the AD requires replacing the unairworthy pitch control assembly with an airworthy unit. This amendment is prompted by reports of failure of the tail rotor pitch control assembly due to improperly lubricated bearings on the RHC Model R22 helicopters. Although there have been no reported failures on the RHC Model R44 helicopters, the design of the tail rotor pitch control assembly makes it susceptible to the same failures as have occurred on the Model R22 helicopters. The actions specified by this AD are intended to detect corrosion of the bearings and to prevent bearing failure and subsequent loss of directional control of the helicopter.
AD 2003-04-15 · published Feb 27, 2003, effective Feb 27, 2003
Sikorsky Aircraft Corporation Model S-76A, B, and C Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters. This action requires determining the manufacturer of a certain part-numbered rotor brake disc (RBD) and if the manufacturer is Parker Hannifin Corporation (PHC), re-identifying the RBD as appropriate. This action also requires before the first flight of the next day following any day in which a certain RBD was used, visually inspecting the RBD for a crack. If a crack is found, this AD also requires replacing the RBD with an airworthy RBD or deactivating it as applicable depending on the nature of the crack. This amendment is prompted by the discovery that certain RBDs manufactured by PHC were improperly heat treated resulting in "soft" RBDs that have an increased wear rate compared to those heat treated in accordance with the type design requirement. Further investigation reveals that "soft" RBDs develop cracks more frequently than previously manufactured RBDs. The actions specified in this AD are intended to prevent failure of the RBD, damage to the rotor blades and nearby hydraulic and fuel lines, and subsequent loss of control of the helicopter.
AD 2002-25-51 · published Feb 28, 2003, effective Mar 17, 2003
Agusta S.p.A. Model A109E Helicopters
This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (EAD) 2002-25-51, sent previously to all known U.S. owners and operators of the specified Agusta S.p.A. (Agusta) helicopters by individual letters. This Airworthiness Directive (AD) requires reducing the tail rotor (T/R) blade life limit and modifying and re-identifying the T/R hub and grip assembly. It also clarifies the never-exceed speed (Vne) restrictions and modifies the T/R visual inspection intervals. The actions specified by this AD are intended to prevent fatigue failure of the T/R blade and subsequent loss of control of the helicopter.
AD 2003-04-12 · published Feb 28, 2003, effective Apr 4, 2003
Bell Helicopter Textron Canada Limited Model 427 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires modifying the auxiliary fin assemblies and revising the Limitations section of the Rotorcraft Flight Manual (RFM) to reduce the never-exceed speed (Vne) for a tail rotor pedal stop failure. This amendment is prompted by several incidents of main rotor blades contacting the top of the fin that have resulted in an upper tuning weight (weight) becoming loose. The actions specified by this AD are intended to prevent a main rotor blade from striking an auxiliary fin, loss of a tuning weight, impact with a tail or main rotor blade, and subsequent loss of control of the helicopter.
AD 2003-04-13 · published Feb 28, 2003, effective Mar 17, 2003
Eurocopter France Model SA341G and SA342J Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocoper) Model SA341G and SA342J helicopters. This action requires modifying an electric hoist (hoist) junction box (junction box). This amendment is prompted by the discovery of an anomaly affecting the resistor that is located in the junction box. The actions specified in this AD are intended to prevent failure of the hoist emergency load jettison switch, resulting in an inability of the pilot to cut the rescue hoist cable in the event of cable entanglement or other emergency and subsequent loss of control of the helicopter.
AD 2003-04-14 · published Feb 28, 2003, effective Apr 4, 2003
Bell Helicopter Textron Canada (Bell) Model 427 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Bell model helicopters that requires replacing the hydraulic solenoid tee fitting (tee fitting) and tubes. This amendment is prompted by the manufacturer's discovery that tee fittings may be installed improperly and restrict hydraulic fluid flow. The actions specified by this AD are intended to prevent restricted flow of hydraulic fluid to the flight control hydraulic actuators resulting in loss of hydraulic control, excessive stiffness in the flight controls, and a subsequent forced landing of the helicopter.
AD 2003-03-21 · published Feb 5, 2003, effective Feb 20, 2003
Pratt & Whitney Canada PW500 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (PWC) PW500 series turbofan engines. This action requires a one-time visual inspection and re- marking, or in lieu of inspection, replacement of certain part numbers (P/N's) of the flexible fuel tube located between the fuel/oil heat exchanger and the integral fuel control unit-fuel pump. This amendment is prompted by reports of fuel found dripping from engine nacelles caused by leaking flexible fuel tubes. The actions specified in this AD are intended to prevent a fire in the engine nacelle.
AD 2003-03-20 · published Feb 4, 2003, effective Mar 11, 2003
Hartzell Propeller Inc., Model HC-C2YR-4CF Propellers
This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. model HC-C2YR-4CF propellers. This amendment requires the reduction of the original hub and blades certified service (fatigue) life from unlimited hours to 2,000 hours. This amendment is prompted by a reevaluation by Hartzell Propeller Inc. of the original hub and blades service life certification calculations. The actions specified by this AD are intended to prevent fatigue failure of the original propeller hub and blades which may result in loss of airplane control.
AD 2003-04-01 · published Feb 11, 2003, effective Mar 18, 2003
Hartzell Propeller Inc., Model HD-E6C-3B/E13890K Propellers
This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. HD-E6C-3B/E13890K propellers. This amendment requires the reduction of the original hub certified service (fatigue) life from unlimited hours to 37,400 flight hours. This amendment is prompted by a reevaluation by Hartzell Propeller Inc. of the D-5108-( ) original hub service life certification calculations. The actions specified by this AD are intended to prevent fatigue failure of D-5108-( ) hubs, which may result in loss of airplane control.
AD 2003-04-22 · published Feb 28, 2003, effective Apr 4, 2003
Hartzell Propeller Inc. Model HD-E6C-3B/E13890K Propellers
This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. model HD-E6C-3B/E13890K propellers with certain serial numbers of model D-1199-2 propeller control units (PCU's) installed. This amendment requires initial and repetitive inspections for below-limit propeller flight idle blade angles, and, as a terminating action, removal of the affected PCU's from service and performance of a complete Major Periodic Inspection (overhaul) when the applicable time-since-new or time-since-overhaul limit is reached, or when any flight idle blade angle is below limits. This amendment is prompted by a review by Hartzell Propeller Inc. of the model D-1199-2 PCU overhaul procedures, that revealed several dimensional checks and a nondestructive evaluation were not performed on certain serial number PCU's during a Major Periodic Inspection (overhaul). The overhaul procedures are required to comply with the Airworthiness Limitation PCU Major Periodic Inspection (overhaul) directive. The actions specified by this AD are intended to prevent below-limit flight idle propeller blade angles that, if not corrected, could result in degraded aircraft performance and control.
AD 2003-04-23 · published Feb 28, 2003, effective Apr 4, 2003
Hartzell Propeller Inc. Model HC-B3TN-5( ) Propellers
This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. model HC-B3TN-5( ) propellers, with blades part number (P/N) T10176H(B,K)-5 or T10178H(B)-11(R) that are installed on Mitsubishi Heavy Industries, Ltd, MU-2 series airplanes. This amendment requires replacement of those blades with blades of the latest design. This amendment is prompted by a report of in-flight propeller blade separation that caused a severe out-of- balance condition, damage to the airplane, and resulted in engine shutdown and a safe landing. The actions specified by this AD are intended to prevent propeller blade separation, damage to the airplane, and possible loss of the airplane.
AD 2003-04-06 · published Feb 24, 2003, effective Mar 11, 2003
Various Aircraft Equipped With Honeywell Primus II RNZ-850/-851 Integrated Navigation Units
This amendment adopts a new airworthiness directive (AD) that is applicable to various aircraft equipped with a certain Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit. As one alternative for compliance, this action provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV850 Navigation Receiver Module, which is part of the Integrated Navigation Unit. In lieu of accomplishing this inspection, and for aircraft found to have an affected navigation receiver module, this action provides for revising the aircraft flight manual to include new limitations for instrument landing system (ILS) approaches. This action is necessary to ensure that the flightcrew has an accurate glideslope deviation indication. An erroneous glideslope deviation indication could lead to the aircraft making an approach off the glideslope, which could result in impact with an obstacle or terrain. This action is intended to address the identified unsafe condition.
